| 1. |
- Bruhn, Fredrik, et al.
(författare)
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Enabling radiation tolerant heterogeneous GPU-based onboard data processing in space
- 2020
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Ingår i: CEAS Space Journal. - : SPRINGER WIEN. - 1868-2502 .- 1868-2510. ; 12:4, s. 551-564
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Tidskriftsartikel (refereegranskat)abstract
- The last decade has seen a dramatic increase in small satellite missions for commercial, public, and government intelligence applications. Given the rapid commercialization of constellation-driven services in Earth Observation, situational domain awareness, communications including machine-to-machine interface, exploration etc., small satellites represent an enabling technology for a large growth market generating truly Big Data. Examples of modern sensors that can generate very large amounts of data are optical sensing, hyperspectral, Synthetic Aperture Radar (SAR), and Infrared imaging. Traditional handling and downloading of Big Data from space requires a large onboard mass storage and high bandwidth downlink with a trend towards optical links. Many missions and applications can benefit significantly from onboard cloud computing similarly to Earth-based cloud services. Hence, enabling space systems to provide near real-time data and enable low latency distribution of critical and time sensitive information to users. In addition, the downlink capability can be more effectively utilized by applying more onboard processing to reduce the data and create high value information products. This paper discusses current implementations and roadmap for leveraging high performance computing tools and methods on small satellites with radiation tolerant hardware. This includes runtime analysis with benchmarks of convolutional neural networks and matrix multiplications using industry standard tools (e.g., TensorFlow and PlaidML). In addition, a 1/2 CubeSat volume unit (0.5U) (10 x 10 x 5 cm(3)) cloud computing solution, called SpaceCloud (TM) iX5100 based on AMD 28 nm APU technology is presented as an example of heterogeneous computer solution. An evaluation of the AMD 14 nm Ryzen APU is presented as a candidate for future advanced onboard processing for space vehicles.
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| 2. |
- Chasset, Camille, et al.
(författare)
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3-Axis magnetic control : flight results of the TANGO satellite in the PRISMA mission
- 2013
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Ingår i: CEAS Space Journal. - : Springer Science and Business Media LLC. - 1868-2502 .- 1868-2510. ; 5:1-2, s. 1-17
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Tidskriftsartikel (refereegranskat)abstract
- PRISMA implements guidance, navigation and control strategies for advanced formation flying and rendezvous experiments. The project is funded by the Swedish National Space Board and run by OHB-Sweden in close cooperation with DLR, CNES and the Danish Technical University. The PRISMA test bed consists of a fully manoeuvrable MANGO satellite as well as a 3-axis controlled TANGO satellite without any ΔV capability. PRISMA was launched on the 15th of June 2010 on board DNEPR. The TANGO spacecraft is the reference satellite for the experiments performed by MANGO, either with a "cooperative" or "non-cooperative" behaviour. Small, light and low-cost were the keywords for the TANGO design. The attitude determination is based on Sun sensors and magnetometers, and the active attitude control uses magnetic torque rods only. In order to perform the attitude manoeuvres required to fulfil the mission objectives, using any additional gravity gradient boom to passively stabilize the spacecraft was not allowed. After a two-month commissioning phase, TANGO separated from MANGO on the 11th of August 2010. All operational modes have been successfully tested, and the pointing performance in flight is in accordance with expectations. The robust Sun Acquisition mode reduced the initial tip-off rate and placed TANGO into a safe attitude in <30 min. The Manual Pointing mode was commissioned, and the spacecraft demonstrated the capability to follow or maintain different sets of attitudes. In Sun/Zenith Pointing mode, TANGO points its GPS antenna towards zenith with sufficient accuracy to track as many GPS satellites as MANGO. At the same time, it points its solar panel towards the Sun, and all payload equipments can be switched on without any restriction. This paper gives an overview of the TANGO Attitude Control System design. It then presents the flight results in the different operating modes. Finally, it highlights the key elements at the origin of the successful 3-axis magnetic control strategy on the TANGO satellite.
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| 3. |
- Kopp, Alexander, et al.
(författare)
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The Aurora space launcher concept
- 2018
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Ingår i: CEAS Space Journal. - : Springer Science and Business Media LLC. - 1868-2502 .- 1868-2510. ; 10:2, s. 167-187
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Tidskriftsartikel (refereegranskat)abstract
- This paper gives an overview about the Aurora reusable space launcher concept study that was initiated in late-2015/early-2016. Within the Aurora study, several spaceplane-like vehicle configurations with different geometries, propulsion systems and mission profiles will be designed, investigated and evaluated with respect to their technical and economic feasibility. The first part of this paper will discuss the study logic and the current status of the Aurora studies and introduces the first vehicle configurations and their system design status. As the identification of highly efficient structural designs is of particular interest for Aurora, the structural design and analysis approach will be discussed in higher level of detail. A special design feature of the Aurora vehicle configurations is the utilization of the novel thin-ply composite material technology for structural mass reductions. Therefore, the second part of this paper will briefly discuss this technology and investigate the application and potential mass savings on vehicle level within simplified structural analysis studies. The results indicate that significant mass savings could be possible. Finally, an outlook on the next steps is provided.
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| 4. |
- Ott, T., et al.
(författare)
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AOCS design for the ATHENA X-ray telescope : challenges and solutions
- 2018
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Ingår i: CEAS Space Journal. - : Springer-Verlag Wien. - 1868-2502 .- 1868-2510. ; 10:4, s. 519-534
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Tidskriftsartikel (refereegranskat)abstract
- The ATHENA—Advanced Telescope for High-ENergy Astrophysics—mission is currently assessed in a phase A feasibility study as L-class mission in ESA’s Cosmic Vision 2015–2025 plan, with launch foreseen in 2028. Primary mission goal is the mapping of hot gas structures and the determination of their physical properties to search for supermassive black holes. ATHENA is an X-ray telescope with a focal length of 12 m. It has a mass of ~ 7000 kg and it is ~ 15 m high with a diameter of ~ 3 m. The main mass is distributed to the mirror on the one side of the spacecraft and to the science instrument module on the other side of the spacecraft. To achieve its science goals, ATHENA performs a sky survey with precision line-of-sight pointing requirements in the order of arc seconds for absolute pointing and sub-arc seconds for relative pointing in time windows > 1 ks, all at 95% confidence level. That is very demanding for large X-ray telescopes. In addition to the precision pointing requirements, ATHENA cannot violate a certain sun exclusion zone. This is a hard constraint to prevent any stray-light falling onto the instruments, as it would immediately destroy them. The sky survey is defined by an observation plan that is demanding in terms of availability and thus spacecraft agility. The pointing and agility requirements and the fact that ATHENA is a spacecraft with high mass and volume introduce several design challenges for the attitude and orbit control system. This paper presents those challenges, corresponding solutions, and preliminary results, which have been achieved during the phase A study led by Airbus in Friedrichshafen, Germany. The main focus and contribution of this paper are the identification of research and development needs for attitude and orbit control systems to enable the ATHENA mission. In this respect, the ATHENA design challenges are discussed and addressed with the state-of-the-art design methods. This paper concludes with the main identified technology development needs and formulates specific research questions related to practical design problems. In particular, the following attitude and orbit control system design challenges are addressed: autonomous and agile large angle slew manoeuvres with exclusion zones, availability for science observations, precision line-of-sight determination as well as analysis during the design process using the ESA Pointing Error Engineering Tool and pointing control with a hexapod as line-of-sight actuator in the control loop. The last challenge, namely, the hexapod in the control loop, is without precedence in Europe and to the best knowledge of the authors in the world.
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| 5. |
- Schneider, J., et al.
(författare)
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Additive manufacturing of a metallic optical bench—process development, material qualification and demonstration
- 2023
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Ingår i: CEAS Space Journal. - : Springer Nature. - 1868-2502 .- 1868-2510. ; 15:1, s. 55-68
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Tidskriftsartikel (refereegranskat)abstract
- With the large-class science mission ATHENA, the European Space Agency (ESA) aims at exploring the hot and energetic universe with advanced X-Ray technology. As a central component of the telescope, hundreds of silicon pore optic (SPO) modules will be assembled in an optical bench with a diameter of about 2.5 m. Several approaches are under investigation for the manufacturing of this supporting structure, and for handling the challenging constraints with respect to size, geometry and material. In cooperation with ESA, the Fraunhofer IWS is currently investigating the manufacturing of the optical bench made from Ti-6Al-4 V by means of Additive Manufacturing using Laser Metal Deposition (LMD) followed by subtractive finishing. Several development steps have been covered in a holistic manner starting with the system engineering of the production site. The main focus of the activity was on the process development for the Additive Manufacturing as well as the subtractive finishing. Furthermore, the properties of the produced material were also investigated. Within the scope of this publication, a general overview is given about the project related developments, achievements, and flanking activities for solving various challenges. The suitability of the developed technologies and workflows are now being evaluated through the manufacture of a representative, large-scale breadboard.
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| 6. |
- Wei, Jianzheng, et al.
(författare)
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Design and testing of inflatable gravity-gradient booms in space
- 2020
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Ingår i: CEAS Space Journal. - : SPRINGER WIEN. - 1868-2502 .- 1868-2510. ; 12:1, s. 33-41
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Tidskriftsartikel (refereegranskat)abstract
- Inflatable space structures have many advantages such as small size, high reliability, and low cost. Aiming at a gravity-gradient boom for an XY-1 satellite, New Technology Verifying Satellite-1, a slender inflatable boom with low magnetic is presented. First of all, an inflatable boom with six self-supporting thin shells made of carbon and Vectran fiber composite materials on the inner wall was designed for eliminating a magnetic dipole moment and increasing structural stiffness. A precise stowage was designed for a tip mass surrounded by a pair of lightweight honeycomb blocks added on the top of the boom. The stowed boom was tested by sine sweep vibrations with three directions on the ground to verify the reasonable design. The XY-1 satellite which carried the inflatable boom was launched into low orbit. After being stowed state in space for at least 6 months, the inflatable boom orderly unfolded a 2.0 kg tip mass to 3.0 m away in May, 2013. The inflatable boom was successfully deployed from a series of photographs received on the satellite. The results show that this kind of lightweight inflatable boom with self-supporting thin shells can orderly unfold and fulfil the function of gravity-gradient in space for a long time.
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